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Given:

TAS = 210 kt
CAS = 190 kt
Pressure Altitude = 9000 ft

Calculate Mach number:

  • A
    0.34
  • B
    0.31
  • C
    0.32
  • D
    0.28

Mach number = TAS / Speed of sound

Using flight computer matching (TAS = 210 kts) in the outer circle with (CAS = 190 kts) in the inner circle
You can read the temperature in front of 9000 feet = —20C˚

Local speed of sound at —20 ={√(273-20)} x 38.95 = 619 kts
Mach number = 210 / 619 = 0.3392

Closest Answer: 0.34

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